IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0748795
(2010-03-29)
|
등록번호 |
US-8495959
(2013-07-30)
|
발명자
/ 주소 |
- Geisler, Robert L
- Mahaffy, Kevin E
|
출원인 / 주소 |
|
대리인 / 주소 |
Hamre, Schumann, Mueller & Larson, P.C.
|
인용정보 |
피인용 횟수 :
3 인용 특허 :
5 |
초록
▼
A kinetic fireball incendiary munition is provided having an outer shell or bomb casing, one or more incendiary submunitions therein, and an igniter therefore. Each of the submunitions includes an incendiary portion, at least one rocket motor that propels the submunition inside of a target volume, a
A kinetic fireball incendiary munition is provided having an outer shell or bomb casing, one or more incendiary submunitions therein, and an igniter therefore. Each of the submunitions includes an incendiary portion, at least one rocket motor that propels the submunition inside of a target volume, and an oxidizer for the incendiary portion and rocket motor. The submunitions liberate sufficient heat to produce elevated temperatures inside of a target structure to thermalize the contents thereof without creating a substantial overpressure or explosive effect. The incendiary portion includes a solid propellant and, optionally, one or more energetic materials selected from the group consisting of phosphorous, boron, magnesium, aluminum, Fluorinert™-aluminum and BKNO3. The incendiary submunition may be in the shape of a ball or a circular disk with a rocket motor therein. The circular disk-shaped incendiary munition is provided with an outer layer of an insulation which is bonded to the propellant/incendiary material. A portion of the insulation on the top and bottom of the disk is weakened so as to break away when the top and bottom surfaces are ignited. In place of the rocket motor, the submunition may incorporate one or more barrels embedded in the incendiary material with a powder charge and projectile in each barrel. Ignition of the incendiary material results in detonation of the powder charge which propels projectiles radially outwardly and upwardly causing damage to containers of chemical/biological materials.
대표청구항
▼
1. An incendiary munition for thermalizing an interior volume of a target structure, said incendiary munition having an outer shell or bomb casing, one or more incendiary submunitions inside of said shell or bomb casing, comprising: each incendiary submunition includes an incendiary portion and one
1. An incendiary munition for thermalizing an interior volume of a target structure, said incendiary munition having an outer shell or bomb casing, one or more incendiary submunitions inside of said shell or bomb casing, comprising: each incendiary submunition includes an incendiary portion and one or more rocket motors, said rocket motor being capable of propelling the submunition inside the target structure, and a propellant for the rocket motor,said submunition containing an internal oxidizer for the incendiary portion and the rocket motor propellant, thereby facilitating ignition and heating from the submunition as well as from the rocket motor,the incendiary portion and the rocket motor together liberate sufficient heat to produce elevated temperatures inside of the target structure to thermalize the interior of the target structure without creating a substantial overpressure or explosive effect. 2. The incendiary munition of claim 1, wherein the submunition is formed at least in part from the incendiary portion that includes solid propellant mixed with the oxidizer. 3. The incendiary munition of claim 2, wherein the solid propellant further contains one or more energetic materials selected from the group consisting of phosphorous, boron, magnesium, aluminum, perfluorocarbon liquid-aluminum and BKN03. 4. The incendiary munition of claim 1, wherein at least a part of the incendiary portion forms an outer exposed surface of the submunition. 5. The incendiary munition of claim 1, wherein a nozzle in the rocket motor is positioned to discharge propellant gases outwardly from the submunition, thereby propelling the submunition within the target structure. 6. The incendiary munition of claim 1, wherein the propellant for the rocket motor comprises a solid propellant mixed with the oxidizer, and the rocket motor includes a rocket nozzle. 7. The incendiary munition of claim 6, wherein the rocket motor is formed integral with the incendiary portion of the submunition. 8. The incendiary munition of claim 6, wherein the rocket motor is formed inside of the submunition by forming a cavity inside of the solid propellant in an inner portion of the submunition. 9. The incendiary munition of claim 8, wherein a hole in the solid propellant extending from said cavity to an outer surface of the submunition defines the rocket nozzle. 10. The incendiary munition of claim 9, wherein the hole is lined with a non-flammable material. 11. The incendiary munition of claim 1, wherein the submunition is substantially spherically shaped, with one or more of the rocket motors integrally formed inside of the substantially spherically shaped submunition. 12. The incendiary munition of claim 1, wherein the submunition is generally disk-shaped, with one or more of the rocket motors integrally formed inside of the generally disk-shaped submunition. 13. The incendiary munition of claim 12, wherein the disk-shaped submunition contains at least two of the integrally formed rocket motors, each of said rocket motors having one or more nozzles pointed in different directions. 14. The incendiary munition of claim 13, wherein a first and second of the rocket motors fire sequentially. 15. An incendiary submunition for thermalizing an interior volume of a target structure, comprising: an incendiary portion;one or more rocket motors inside the incendiary portion which are capable of propelling the submunition inside of the target structure;a propellant for the rocket motor;an oxidizer for both the incendiary portion and for the rocket motor propellant, thereby facilitating the liberation of heat from both a burning outer surface of the submunition and from the rocket motor;the incendiary portion and the rocket motor liberate sufficient heat to produce elevated temperatures inside of the target structure to thermalize the interior of the target structure without creating a substantial overpressure or explosive effect during combustion. 16. The incendiary submunition of claim 15, wherein the incendiary portion is formed at least in part from a solid propellant optionally containing an energetic material selected from the group consisting of phosphorous, boron, magnesium, aluminum, and fluorocarbon liquid aluminum and BKN03, and the outer surface of the submunition comprises the solid propellant. 17. The incendiary submunition of claim 16, wherein the rocket motor is defined by a cavity formed in the solid propellant comprising the incendiary portion of the submunition, with a hole extending from the cavity to an outer surface of the submunition so as to define a rocket nozzle. 18. The incendiary submunition of claim 15, wherein the rocket motor is disposed within the incendiary portion of the submunition. 19. The incendiary submunition of claim 15, wherein the submunition is in the shape of a sphere, with the rocket motor formed inside of the sphere. 20. The incendiary submunition of claim 15, wherein the submunition is in the form of a circular disk with the rocket motor formed inside of the circular disk, the rocket motor having a nozzle extending from an inside cavity of the rocket motor to an outer surface of the circular disk. 21. The incendiary submunition of claim 20, wherein an insulation layer is bonded to an outer surface of the circular disk, and a portion of the insulation layer on a top and bottom of the circular disk is weakened so as to blowout when top and bottom surfaces of the incendiary portion are ignited. 22. The incendiary submunition of claim 21, wherein the insulation layer comprises a member selected from the group consisting of an ethylene propylene diene rubber and hydroxyl terminated polybutadiene filled with silica particles. 23. The incendiary submunition of claim 21, wherein inters are positioned on the top and bottom surfaces of the incendiary portion and blow off the portions of the insulation layer on the top and bottom surfaces. 24. The incendiary submunition of claim 21, wherein a plurality of said incendiary submunitions are sequentially ignited inside of a target structure, whereby to raise the temperature therein to as high as 170 QOF for about five minutes. 25. An incendiary submunition for thermalizing an interior volume of a target structure, comprising: an incendiary portion;one or more rocket motors inside the incendiary portion;a propellant for the rocket motor; anda solid oxidizer in both the incendiary portion and the rocket motor propellant. 26. The incendiary submunition of claim 25, wherein the incendiary portion comprises a solid propellant; and the rocket motor is formed by a cavity and a rocket nozzle in the solid propellant of the incendiary portion, and the rocket motor propellant comprises the solid propellant of the incendiary portion. 27. The incendiary submunition of claim 25, wherein the incendiary portion comprises a solid propellant; and the rocket motor is embedded within the solid propellant of the incendiary portion. 28. The incendiary submunition of claim 25, wherein the submunition has a spherical shape, and the incendiary portion forms an outer exposed surface of the sphere. 29. The incendiary submunition of claim 25, wherein the incendiary portion has a disk shape, and further comprising at least two of the rocket motors, each rocket motor having a rocket nozzle, and the rocket nozzles point in different directions. 30. The incendiary submunition of claim 29, further comprising an insulation layer surrounding the incendiary portion.
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